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    Combustor wall with tapered cooling cavity
    42.
    发明授权
    Combustor wall with tapered cooling cavity 有权

    公开(公告)号：US10047958B2

    公开(公告)日：2018-08-14

    申请号：US15026761

    申请日：2014-10-06

    Applicant: United Technologies Corporation

    Inventor： Nurhak Erbas-Sen ,  Frank J. Cunha

    IPC: F23R3/06 ,  F23R3/00 ,  F23R3/08

    Abstract: A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.

    COOLING AN IGNITER BODY OF A COMBUSTOR WALL
    45.
    发明申请
    COOLING AN IGNITER BODY OF A COMBUSTOR WALL 审中-公开
    冷却煤气炉壁炉的烟雾

    公开(公告)号：US20160305325A1

    公开(公告)日：2016-10-20

    申请号：US15100363

    申请日：2014-12-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

    IPC: F02C7/18 ,  F02C7/264

    CPC classification number: F02C7/18 ,  F02C7/264 ,  F02C7/266 ,  F05D2260/20 ,  F23R3/005 ,  F23R3/06 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁。 燃烧器壁包括壳体，隔热罩和环形体。 主体在内表面和外表面之间横向延伸。 内表面在燃烧器壁中限定了点火器孔。 外表面垂直在隔热罩和外壳之间。 壳体限定第一冷却孔，空气通过该第一冷却孔被引导以撞击外表面。

    COOLING A QUENCH APERTURE BODY OF A COMBUSTOR WALL
    46.
    发明申请
    COOLING A QUENCH APERTURE BODY OF A COMBUSTOR WALL 审中-公开
    冷却一个燃烧器墙的哨孔孔

    公开(公告)号：US20160290643A1

    公开(公告)日：2016-10-06

    申请号：US15035356

    申请日：2014-12-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

    IPC: F23R3/00 ,  F02C7/24 ,  F02C7/18 ,  F23R3/04

    CPC classification number: F23R3/002 ,  F02C7/12 ,  F02C7/18 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/30 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/231 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 涡轮发动机组件的燃烧器壁包括外壳，隔热罩和与外壳和隔热罩接合的环形体。 环形体延伸穿过燃烧器壁。 环形体至少部分地沿着穿过燃烧器壁的中心线限定了淬火孔。 环形体还至少部分地限定与淬火孔径流体连通的冷却孔。 冷却孔的至少一部分相对于中心线从淬火孔径向向外延伸。

    COMBUSTOR WALL HAVING COOLING ELEMENT(S) WITHIN A COOLING CAVITY
    48.
    发明申请
    COMBUSTOR WALL HAVING COOLING ELEMENT(S) WITHIN A COOLING CAVITY 审中-公开
    在冷藏室内具有冷却元件的蒸气墙

    公开(公告)号：US20160238249A1

    公开(公告)日：2016-08-18

    申请号：US15025455

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frank J. Cunha ,  Stanislav Kostka, JR.

    IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06

    CPC classification number: F23R3/002 ,  F02C7/18 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  F23R2900/03045

    Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a cooling element. The shell defined a first set of apertures. The heat shield defines a second set of apertures. The cooling element extends between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield. The tapered cavity is fluidly coupled with the first and the second sets of apertures. The cooling element is thermally coupled to one of the shell and the heat shield.

    Abstract translation: 为涡轮发动机提供燃烧器壁。 燃烧器壁包括外壳，隔热罩和冷却元件。 外壳限定了第一组孔。 隔热罩限定第二组孔。 冷却元件在外壳和隔热罩之间延伸在限定在外壳和隔热罩之间的锥形冷却腔内。 锥形空腔与第一组和第二组孔流体连接。 冷却元件热耦合到外壳和隔热罩中的一个。

    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    49.
    发明申请
    VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    VENA CONTRACTA发动机燃油涡轮增压通道

    公开(公告)号：US20160201908A1

    公开(公告)日：2016-07-14

    申请号：US14910856

    申请日：2014-06-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Christopher Drake ,  Frank J. Cunha ,  Stanislav Kostka, JR. ,  Jonathan M. Jause ,  Russell B. Hanson

    IPC: F23R3/00 ,  F23R3/06 ,  F23R3/26 ,  F02C7/18

    CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/04 ,  F23R3/045 ,  F23R3/26 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括：喷嘴，其包括沿轴线的内周边。 内周边包括围绕轴的流动引导件。 用于燃气涡轮发动机的燃烧器的壁组件包括具有沿轴线的第一内周边的支撑壳体。 壁组件还包括具有沿着轴线的第二内周边的衬板，第二内周包括围绕轴的螺旋形流动引导件。 减少在燃气涡轮发动机的燃烧器衬板中的再循环进入稀释通道的方法包括对稀释通道进行轮廓化，以匹配流过其中的流体的天然收缩膜。

    FUEL INJECTOR GUIDE(S) FOR A TURBINE ENGINE COMBUSTOR
    50.
    发明申请
    FUEL INJECTOR GUIDE(S) FOR A TURBINE ENGINE COMBUSTOR 审中-公开
    燃油喷射器指南用于涡轮发动机燃烧器

    公开(公告)号：US20160169522A1

    公开(公告)日：2016-06-16

    申请号：US14939667

    申请日：2015-11-12

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka

    IPC: F23R3/28

    Abstract: A fuel injector guide is provided for a turbine engine combustor. The fuel injector guide includes a tubular base, an annular flange, a plurality of ribs and a flow turbulator. The base extends along an axis between first and second ends. The flange extends radially out from the base at the second end. The ribs are disposed around the base and extend axially out from the flange towards the first end. The flow turbulator is disposed between an adjacent pair of the ribs.

    Abstract translation: 为涡轮发动机燃烧器提供燃料喷射器引导件。 燃料喷射器引导件包括管状基座，环形凸缘，多个肋和流动紊流器。 底座沿着第一和第二端之间的轴线延伸。 凸缘在第二端从底座径向伸出。 肋围绕基部设置并且从凸缘朝向第一端轴向延伸。 流动紊流器设置在相邻的一对肋之间。

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